Expendable-piston tube missile launcher



F. A. OYHUS EXPENDABLE-PISTON TUBE MISSILE LAUNCHER June 2, 1964 FREDERICK AOYHUS INVENTOR ATTORNEYS 3 Sheets-Sheet 1 Filed Aug. 8, 1961 June 2, 1964 QYHUS 3,135,161

EXPENDABLE-PISTON TUBE MISSILE LAUNCHER Filed Aug. 8, 1961 3 Sheets-Sheet 2 OYHUS FREDERICK HQIVENTOR BY MiG-W ATTORNEYS June 2, 1964 F. A. OYHUS 3,135,161

EXPENDABLE-PISTON TUBE MISSILE LAUNCHER Filed Aug. 8, 1961 3 Sheets-Sheet 3 FREDERICK A.

OYHUS INVENTOR ATTORNEYS United States Patent 3,135,161 EXPENDABLE-PISTON TUBE MISSILELAUNCHER Frederick A. Oyhus, Rockville, Md., assignor to the United States of America as represented by the Secretary 0f the Navy Filed Aug. 8, 1961, Ser. No. 130,196

4 Claims. (Cl. 89-1.7)

This invention relates generally to missile launching apparatus; more particularly, it relates to an improved launcher for launching a comparatively large guided missile with a minimum time for preparation.

The most common method at present for launching guided missiles from a surface ship is to mount each missile upon a launching arm structure, from which it is launched under its own power.

The time required for moving the missile from storage, placing it on the launcher, and firing it, while not too great in the case of an individual launching, is quite substantial when a large number of missiles must be dispatched toward a target. A

further problem in utilizing launching arm apparatus is great number of missiles in as short a time as possible is obvious, and the danger attending the time lag resulting when a malfunctioning missile must be replaced on the launcher is likewise evident. In an attempt to increase the amount of missile firepower during a given time interval the use of individual missile launching tubes has recently been proposed.

The launching tube concept involves the placing of a great number of individual, tube type launchers in the deck of a ship, each tube containing one missile. The tube-type launchers may be independently activated, and need be fired in no particular sequence. Thus, missiles may be launched consecutively with very little time lag between launchings, or a number of missiles may be launched simultaneously to give a barrage firing eifect. Further if one particular missile should malfunction it is not necessary that it be removed from the launcher and replaced by another before the launching operation can continue. Rather, the faulty missile is merely bypassed, and another is launched in its stead. Thus, the number of missiles that may be launched in a given time to repulse an attack is optimized, and is limited only by the capability of the electronic fire control equipment to handle them.

In tube launchers of the type to which this invention relates the missile is catapulted from the tube, after which its engine is ignited. The missile then continues under its own power to intercept the target. In order to satisfy the requirements for successfully launching a guided missile in this manner a tube launcher must possess several characteristics. The catapulting capability of the launcher must be sufiicient to insure that the missile is propelled clear of the ship and to an altitude great enough to in sure that after ignition its motor will have time to assume propulsion of the missile. Also, a means must be provided to transmit prefiight information to the missile while it is within the launching tube, and safety apparatus should be included to insure that the missile remains locked in position until just prior to launching time. In addition, the launcher should be easy to load under conditions at sea, the missile should be protected from adverse atmospheric conditions, and the reliability of the whole system should be very high. The subject invention is directed to a tube-type missile launcher capable of satisfying each of these requirements.

The principal object of this invention, therefore, is to Patented June 2, 1964 provide a tube-type launcher so constructed as to be capable of launching a comparatively large guided missile from a surface ship under combat conditions at sea, with a minimum time required for preparation.

A further object of the invention is to provided tubetype missile launcher so constructed that the launching tube thereof may also be utilized to transport the missile to the launcher, and to store the missile under sealed conditions until it is launched.

It is also an object of this invention to provide a tubetype missile launcher having means to supply preflight information in the form of electrical energy to the missile before it is launched, said means being so constructed that it is automatically disconnected from the missile during the launching operation.

Another object of the invention is to provide a tubetype missile launcher incorporating means to maintain a missile fixed in position until it is desired to launch the same, thereby preventing damage thereto that might result from rough handling.

It is also an object of the invention to provide a tubetype missile launcher that is structurally uncomplicated and that is economical to construct.

Still another object of the invention is to provide a tube-type missile launcher so constructed that it may be operated without undue danger to surround-ing structures and nearby personnel.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with' the accompanying drawings, wherein:

FIG. 1 is a fragmentary elevation, partially in section, showing the tube-type launcher of the invention, with a missile therein, installed in a ship;

FIG. 2 is an enlarged detail section, on the line 2-2 of FIG. 11, showing the construction of the lower end of the launching tube and the manner in which it is connected to the launcher base;

FIG. 3 is a detail elevation taken generally at line 33 in FIG. 2, showing the manner in which the missile is latched to the launching tube structure;

FIG. 4 is a top plan, partially in section, looking into the forward end of the launching tube with the upper seal removed, and showing in particular the configuration of the foam support blocks and the construction of the detachable connector plug unit; and

FIG. 5 is a detail sectional view on the line 5-5 in FIG. 1, showing in particular the construction and operation of the detachable connector plug and the construction of the piston capturing arms.

The present invention relates to a tube-type launcher for launching comparatively large guided missiles, say those measuring about fifteen feet in length. The launcher of the invention includes a cylindrical tube within which is supported the missile to be launched, the tube serving both as a storage vessel for the missile and as a launching tube. The missile is initially secured to the structure of the tube to prevent damage thereto from rough handling, and the tube is sealed at both ends to prevent contamination of the missile by water or other foreign matter. The tube with its encased missile is secured to a launcher base, which base contains-apparatus for supplying high pressure gas to the tube to catapult the missile therefrom. Just prior to launching, the means latching the missile to the tube is released, and preflight information in the form of electrical energy is fed to the missile through a detachable connector plug apparatus.

At launching the launcher base admits a large volume of high pressure gas to the lower end of the tube, which gas acts upon a movable piston disposed within the tube and upon which the missile rests. The piston is propelled through the tube, pushing the missile ahead of it. When the piston reaches the upper end of the tube it is captured by a set of arms and is retained within the tube, while the missile is catapulted a substantial distance into the atmosphere. The connector plug is so constructed that it automatically detaches from the missile during the launching operation.

Referring now to the drawings, a portion of a ship is indicated generally at 2, and includes an upper deck 4, a pair of spaced, horizontal supporting bulkheads 6, and a lower deck 8. The upper deck and the bulkheads have aligned openings and 12, respectively, therein, said openings being disposed about a central axis that is arranged at an angle to the vertical. A supporting cylinder 14 is fitted within the openings 10 and 12 and extends from the top surface of the upper deck to the bottom surface of the lower of the two bulkheads 6. Another supporting cylinder 16, spaced from the cylinder 14, is shown fitted within another set of aligned openings in the top deck and the bulkheads 6, and it is contemplated that in a ship a great many such cylinders would be utilized. The description herein will be limited, however, to the launcher structure as it relates to the supporting cylinder 14, it being understood that the same structure is associated with each supporting cylinder.

guide lying parallel to the central axis of the cylinder and having a plurality of roller wheels 20 secured thereto by pins 22. The guides 18 function to facilitate the insertion through cylinder 14 of a launching tube 24, and to laterally support said tube when it is in position.

As best seen in FIGS. 1 and 2, the lower deck 8 has a plurality of inclined supporting surfaces 26 thereon, one for each launching tube. Mounted upon each surface 26 is a cylindrical base 28, within which is telescoped the lower end of the launching tube 24. The cylindrical base 28 includes a housing 30 having a radially extending flange 32 at its upper end, there being a pair of diametrically disposed, generally V-shaped notches 34 extending downwardly into the housing 30 from the upper end there- 'of an axial distance several times the axial width of the flange 32. Disposed within and extending across the housing 30 centrally thereof is a bulkhead 36, upon which rests an annular metallic seal 38 of V-shapecross-section, the outer diameter of the seal being slightly smaller than the inner diameter of said housing, and the seal lying with its V-shaped cross-section opening toward the longitudinal axis of the housing.

The launching tube 24 has a pair of oppositely-disposed lugs 40 thereon of a size and shape to be received within notches 34. The lugs 40 project from tube 24 sufficiently so that they extend outwardly from housing 30 approximately the same distance as flange 32, and their dimensions measured in the direction of the longitudinal axis of tube 24 are substantially less than the depth of the notches 34, whereby there is space between the opposing surfaces of flange 32 and saidlugs sufficient to permit insertion of a band clamp 42. The clamp 42 is annular in form and is secured in position about housing 30 and between the lugs 40 and flange 32 by a tightening bolt apparatus 44, and fastens the launching tube 24 to said housing.

Disposed within the housing 30 below bulkhead 36 is a pressurized gas storage tank 46, which is supplied with gas through a conduit 48 extending through the wall of the housing 30. A dump valve 50 is connected with tank 46, and passes through bulkhead into the space thereabove. The valve 50 is electrically operated by a battery or other electrical power source, and a switch 52, shown schematically in FIG. 2.

The lower end of launching tube 24 contains missile supporting structure, which includes a cylindrical standard 54 supported by a plurality of circumferentially-spaced plates 56, the plates and the standard being positioned a short distance from the lower end of the tube. The cylindrical standard 54 has a pair of oppositely disposed notches 58 in its upper end, and the inner diameter of the cylinder is just great enough to receive the exhaust nozzle 60 of a guided missile .62. The nozzle 60 has a pair of diametrically-opposed lugs 64 projecting therefrom and positioned to enter the notches 58. The missile is supported axially within the tube 24 by said lugs 64, which rest upon the standard 54 in the notches 58.

The missile is secured to the standard 54 by a pair of latches 66 which engage the lugs 64. The latches are fixed to a shaft 68, which shaft passes through aligned openings 70, 72 and 74 in the tube 24 and standard 54. As shown in FIGS. 2 and 3, one of the latches 66 is attached to the shaft 68 on each side of standard 54, and said latches are so dimensioned that partial rotation of the shaft 68 will engage them with or disengage them from the lugs 64.

The boss 76 surrounds opening 70 in tube24, and an O-ring 78 is disposed within an annular groove in the cylindrical wall defining said opening for sealing the and extends therebetween, whereby activation of the motor 82 will cause the shaft 68 to rock, thereby causing the latches 66 to swing either into or out of engagement with the lugs 64, depending upon the direction of rotation of the motor shaft.

Referring again to FIG. 1, the missile 62 is a selfcontained, rocket propelled missile, and includes four longitudinally extending dorsal fins 92 and a like number of folding tail fins 94. The tail fins 94 are similar in construction to those shown in US. Patent No. 2,925,966

and, as is best shown in FIG. 2, are arranged so that two adjacent fins fold toward one another in an overlapping manner. The missile is supported laterally within the tube 24 by fourarcnate support blocks 96 of a very lightin-weight foam material. As shown in FIGS. 1 and 4, the blocks 96 are of such length that they extend slightly beyond the opposite ends of the dorsal fins of the missile,

and are of such Width that they extend between adjacent dorsal fins. The blocks also extend radially fromthe outersurface of the missile to the inner surface of the launching tube, and they have longitudinally-extending V-shaped grooves 97 in their outer surfaces for further reducing their weight.

As hereinbefore mentioned, the missile is propelled fromthe launching tube by the action of compressed gas upon a piston. Referring again to FIG. 2, a piston 98 is shown disposed between the lower end of the missile 62 and standard supporting plates 56. The piston includes an outer cylindrical shell 100, a longer inner cylindrical shell 102, an annular plate 104, and a frustoconical member 106. The shells 100 and 102 are arranged concentrically with their upper edges lying in the sameplane, and the annular plate 104 is welded in position therebetween. Frusto-conical member 106 has an inturned lip 108 of a size to snugly fit about the lower end of the shell 102, and is also welded in position. The space within the piston is occupied by a lightweight foam material 110, and an annular rubber gasket 112 is secured by rivets 114 to the outer shell for sealing the piston relative to the inner wall of launching tube 24. The gasket 112 includes a cylindrical portion 116 and an integrally-formed, hollow, enlarged portion 118 at its lower end. A suitable foam material for the annular foam ring and support blocks 96 is the product known as Lockfoam Type C608.

engaging the aft end face 122 of the missile. An annular support ring 124 is welded to the inner surface of launching tube 24 adjacent the upper ends of plates 56, and the enlarged portion of the gasket 112 rests thereon when the missile is positioned as shown in FIG. 2. In this manner the seal 112 also functions partially as a shock absorber while the missile is in storage within tube 24.

Attached to the annular plate 104, as by welding, are two longitudinally-extended fin clips 126 (FIGS. 1 and 2), each having a bifurcated upper end. The clips are positioned to engage each of the overlapped pairs of fins 94, and function to retain the fins in their folded positions until the missile has cleared the launching tube.

Referring now to FIGS. 4 and 5, prefiight information in the form of electrical energy is supplied to the missile 62 through a conduit 128 and a detachable plug 130. The electrical connection portion of the plug 130 is of the pronged type, and may be of any suitable configuration. The pronged plug is plugged into a suitable mating socket (not shown) contained Within a recess 132 near the forward end of the missile. The conduit 128 extends from the missile to the forward end of the launching tube 24,

-where it passes over a roller 134 suitably mounted within a notch in the tube; it then passes to a junction box 136 secured to the outer surface of tube 24, where it is connected with a supply conduit 138 (FIG. 1) detachably connected with the junction box by suitable means, and extending from the tube 24 to the ships electrical energy distribution system (not shown).

The plug 130 is of a known type, and is so constructed that it will automatically disengage from the missile as the latter is launched. The plug includes a body 140, to

which is connected the conduit 128. Disposed about the body 140 is a bifurcated lever 142, the spaced arms of which are pivotally attached to each side of the body near the upper edge thereof by pins 144. The outer ends of said arms carry latches 146 which are arranged to face away from the direction of travel of the missile. The latches 146 are normally engaged with a pair of pins 148 projecting from the side walls of recess 132, whereby the plug 130 is secured to the missile. The lever 142 has a projecting arm 150 thereon carrying an eye bolt 152 at its outer end, and a thin wire cable 154 is fastened to said eye bolt and extends over roller 134 to the exterior of tube 24, where it is connected to the upper end of a powerful coil spring 156. The major portion of the spring 156 is contained within a housing 158 extending down the exterior of the launching tube 24, the opposite end of said spring being secured to the tube 24 at the bottom of said housing. The spring is normally under tension, and hence the pull exerted thereby upon cable 154 acts through the lever 142 to insure that the latches 146 thereof remain engaged with pins 148. The electrical conduit 138 is secured at several points within the tube 24 to the wire cable 154 by suitable fastening rings 160.

When the missile 62 is launched from tube 24 the piston 98 would normally also be expelled from the tube, as it would be unrestrained. This, however, would create a dangerous situation for surrounding personnel and structures, and hence a means-is provided for retaining the piston within the tube.

Attached at four points spaced about the circumference of the upper end of tube 24 are piston capturing arms 162. As is best seen in FIGS. 4 and 5, each arm 162 is attached to one of four radially projecting, bifurcated supports 164, which are welded to the exterior of the launching tube 24 at its upper end. The arms each include a body portion 166, a radially-directed arm portion168, and a rearwardly-directed arm portion 170. The body portion 166 is positioned between the arms of bifurcated support 164, and is attached thereto by two spaced bolts 172 and 174. The bolt 172 is removable to permit the arm 162 to be pivoted clear of the mouth of the launching tube (as shown by phantom lines in FIG. 5) to facilitate insertion of the missile therein. The four arms 162 are each positioned to register with one of the V-shaped grooves 97 in the foam blocks 96, and are circumferentially spaced from the roller 134.

After the missile 62 has been inserted into and secured within the launching tube 24, and after the plug has been placed in position, the ends of the tube are sealed by an upper seal 176 and a lower seal 178, both of which are made of a suitable material such as reinforced polyethylene. Each seal has an axially-directed flange to aid in positioning it, and the upper seal 176 is cut out at 180 to fit around conduit 128 and cable 154.

The seals are both secured in position by a suitable resin,

and liquid rubber is flowed about cutout 180 to seal the space about the conduit and cable.

In operation, the launcher of the invention performs as follows. First, while electrical energy is supplied through plug- 130 to the missile, the motor 82 is activated to rock the latches 66 away from the lugs 64, thus freeing the missile from the standard 54. When the prefiight program of the missile is completed and the launching time is at hand switch 52 is closed, actuating dump valve 50. A great volume of pressurized gas (such as air or nitrogen) previously stored in tank 46 is then suddenly released into the area between annular metallic seal 33 and seal 178. The later is immediately ruptured, and the gas then acts upon the piston 98 and the aft end of the missile, propelling the two upwardly at an ever-increasing velocity. The seal 114 prevents undue leakage of the gas past the piston, although a moderate amount of leakage is to be expected. Similarly, the snug fit between the aft end of the missile and the piston prevents undue leakage at this point.

Proceeding now to the plug 130, as the missile moves upwardly in the launching tube the seal 176 is first ruptured, while the spring 156 collapses at a velocity as great as that of the missile, thus keeping cable 154 taut. A large loop 182 is provided in conduit 128 external of the launching tube to permit it to travel with the upper end of the spring. As the plug 130 passes the upper end of the tube 24 tension on the arm 1511, created by cable 154, is suddenly reversed, thus tending to pivot the lever 142 rearwardly to thereby release the latches 146 from the pins 148. The lever 142 is provided with a rearwardly-extending arm 184, the free end of which seats in a detent 186 in the missile as the lever tilts rearwardly. The action of arm 184 lifts the plug 146 almost radially from the missile, thus disconnecting the plug from the missile. When the plug is disconnected, the spring 156 immediately causes it to move out of the way, the plug assembly then coming to rest against a U-shaped bracket 188 welded to the launching tube and extending about the roller 134.

The missile continues upwardly until it is clear of the launching tube 24. At this point the lightweight foam blocks 96 fall harmlessly away. When the piston 93 reaches the arms 162 it is retained thereby, it normally being damaged beyond reuse by this action. The missile continues upwardly from the thus stopped piston, and the folded fins 94 slide free of retainer 126. The fins are then caused to be erected by a suitable apparatus, such as that shown in U.S. Patent No. 2,977,880.

After the missile has reached an altitude of about 60 feet its rocket motor is ignited, and it then begins its powered flight. The launching tube, having served its function, is then either fitted with another missile while on the ship, or it is removed and returned to the factory for reloading.

It should be noted that in the invention the launching tube 24 need not be a specially machined tube, but can be constructed from ordinary steel tubing. This is possible because of the foam support blocks 96 and the loosefitting piston 98. The foam blocks are of a material having some resilience in the presence of an unsmooth sur- 7 face, and they hence serve to support the missile even in a Wide tolerance tube. Piston 98, because it is sealed by the large fluid pressure-type seal 112, is thus useable in a wide tolerance tube. Hence, the need for a specially formed and carefully machined steel tube is eliminated, and small dents occurring in handling and mounting the tube Will not significantly damage its operating efiiciency.

Obviously, many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be prac ticed otherwise than as specifically described.

What is claimed is:

1. In combination with a reaction motor propelled aerial missile having a nozzle, a missile launcher including an upwardly directed supporting cylinder having a plurality of longitudinally-extending guides therein, a base positioned below said cylinder in alignment with the longitudinal axis thereof, a cylindrical launching tube disposed within said supporting cylinder and detachably secured at its lower end to said base, said guides each having rollers for facilitating the insertion of said launching tube into said supporting cylinder, support means mounted within said tube at the lower end thereof and including a centrally positioned cylindrical standard, an axially shiftable piston disposed within the lower end of said tube above said support means and in sealed relationship with said tube, said piston engaging the aft end surface of the missile in the tube and said standard engaging the nozzle, a plurality of elongated, arcuate blocks of lightweight material disposed about the missile between airfoil surfaces thereof and extending between the missile and the inner surface of said tube, and a stationary, remotely controlled source of pressurized gas disposed within said base and adapted to discharge into said launching tube beneath said piston for urging the latter upwardly through said tube to thereby catapult the missile therefrom, said source being structurally independent of said missile whereby it may be repeatedly utilized.

2. The combination recited in claim 1, including a pair of oppositely projecting lugs on the missile nozzle, a rtatable shaft extending through said standard and through the outer wall of said base, a pair of latch members secured to said shaft on either side of said standard and arranged to alternately engage and disengage said lugs,

and means for rotating said shaft.

3. The combination recited in claim 1, including frangible seals disposed within said launching tube at the upper and the lower ends thereof for sealing the missile contained therein from external elements.

4. In combination with an aerial missile having a nozzle, a device for launching said missile, comprising a base, a

cylindrical launching tube detachably secured to said base, an axially shiftable piston having a centrally located opening therein, said piston being disposed within the lower end of said tube in sealed relationship therewith, said aerial missile being disposed within said tube and in engagement with said piston, such that the nozzle of the missile is received through said centrally located opening, said missile having a plurality of longitudinally extending airfoil surfaces thereon, a plurality of elongated, structurally independent arcuate blocks of lightweight material disposed about said missile between said airfoil surfaces and extending between the missile and the inner surface of said tube, and a stationary remotely controlled source of pressurized gas disposed within said base remote from the launching tube and adapted to discharge into said launching tube beneath said piston with sufficient pressure to urge the latter upwardly in said tube to thereby catapult said missile therefrom, said source being structurally independent of said missile whereby it may be repeatedly utilized, a junction box on the exterior of said launching tube near the upper end thereof, an electrical conduit extending from said box into said tube and having an electrical plug thereon for connection with said missile, a resilient member mounted on the exterior of said tube, a roller positioned at the forward end of said tube, and a cable connected with said resilient member and said plug member and passing over said roller, whereby said plug may be disconnectedfrom said missile upon catapulting of the missile from said tube.

References Cited in the file of this patent UNITED STATES PATENTS 548,374 Lloyd et a1 Oct. 22, 1895 2,064,503 Temple Dec. 15, 1936 2,115,028 Logan Apr. 26, 1938 2,349,009 Schwab May 16, 1944 2,426,610 Hopkins Sept. 2, 1947 2,440,723 MacDonald May 4, 1948 2,657,630 Blacker Nov. 3, 1953 2,710,384 Dupre et a1. June 7, 1955 2,777,391 McNally Jan. 15, 1957 2,788,744 Donner Apr. 16, 1957 2,951,421 Katzen Sept. 6, 1960 2,989,899 Siegel et a1. June 27, 1961 3,038,383 Von Tiesenhausen June 12, 1962 3,084,599 Webster et a1 Apr. 9, 1963 3,084,600 Walker Apr. 9, 1963 3,088,374 Guyant et a1. May 7, 1963 3,089,388 Webster et a1 May 14, 1963 FOREIGN PATENTS 502,560 France Feb. 24, 1920 

1. IN COMBINATION WITH A REACTION MOTOR PROPELLED AERIAL MISSILE HAVING A NOZZLE, A MISSILE LAUNCHER INCLUDING AN UPWARDLY DIRECTED SUPPORTING CYLINDER HAVING A PLURALITY OF LONGITUDINALLY-EXTENDING GUIDES THEREIN, A BASE POSITIONED BELOW SAID CYLINDER IN ALIGNMENT WITH THE LONGITUDINAL AXIS THEREOF, A CYLINDRICAL LAUNCHING TUBE DISPOSED WITHIN SAID SUPPORTING CYLINDER AND DETACHABLY SECURED AT ITS LOWER END TO SAID BASE, SAID GUIDES EACH HAVING ROLLERS FOR FACILITATING THE INSERTION OF SAID LAUNCHING TUBE INTO SAID SUPPORTING CYLINDER, SUPPORT MEANS MOUNTED WITHIN SAID TUBE AT THE LOWER END THEREOF AND INCLUDING A CENTRALLY POSITIONED CYLINDRICAL STANDARD, AN AXIALLY SHIFTABLE PISTON DISPOSED WITHIN THE LOWER END OF SAID TUBE ABOVE SAID SUPPORT MEANS AND IN SEALED RELATIONSHIP WITH SAID TUBE, SAID PISTON ENGAGING THE AFT END SURFACE OF THE MISSILE IN THE TUBE AND SAID STANDARD ENGAGING THE NOZZLE, A PLURALITY OF ELONGATED, ARCUATE BLOCKS OF LIGHTWEIGHT MATERIAL DISPOSED ABOUT THE MISSILE BETWEEN AIRFOIL SURFACES THEREOF AND EXTENDING BETWEEN THE MISSILE AND THE INNER SURFACE OF SAID TUBE, AND A STATIONARY, REMOTELY CONTROLLED SOURCE OF PRESSURIZED GAS DISPOSED WITHIN SAID BASE AND ADAPTED TO DISCHARGE INTO SAID LAUNCHING TUBE BENEATH SAID PISTON FOR URGING THE LATTER UPWARDLY THROUGH SAID TUBE TO THEREBY CATAPULT THE MISSILE THEREFROM, SAID SOURCE BEING STRUCTURALLY INDEPENDENT OF SAID MISSILE WHEREBY IT MAY BE REPEATEDLY UTILIZED. 